CN107849983B - Turbine engine exhaust shell with improved service life - Google Patents

Turbine engine exhaust shell with improved service life Download PDF

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Publication number
CN107849983B
CN107849983B CN201680042755.5A CN201680042755A CN107849983B CN 107849983 B CN107849983 B CN 107849983B CN 201680042755 A CN201680042755 A CN 201680042755A CN 107849983 B CN107849983 B CN 107849983B
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CN
China
Prior art keywords
exhaust casing
arm
hub
reinforcing member
cover
Prior art date
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Active
Application number
CN201680042755.5A
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Chinese (zh)
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CN107849983A (en
Inventor
巴普蒂斯特·玛丽·奥班·皮埃尔·茹伊
波然德·纪尧姆·罗宾·佩拉顿
塞巴斯蒂安·简·劳伦特·普莱斯特尔
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/30—Exhaust heads, chambers, or the like
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/13—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having variable working fluid interconnections between turbines or compressors or stages of different rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/10—Purpose of the control system to cope with, or avoid, compressor flow instabilities
    • F05D2270/101—Compressor surge or stall
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/11—Purpose of the control system to prolong engine life
    • F05D2270/114—Purpose of the control system to prolong engine life by limiting mechanical stresses
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/502—Thermal properties
    • F05D2300/5021—Expansivity
    • F05D2300/50212—Expansivity dissimilar
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)
  • Exhaust Silencers (AREA)
  • Control Of Turbines (AREA)

Abstract

The present invention relates to a kind of exhaust casings, turbogenerator for aircraft, the exhaust casing includes: lantern ring (4), hub (5), the hollow arm (63) that the lantern ring (4) is connected to the hub (5), and opening member (3), the opening member are located at the outlet (30) on lantern ring (4) and being suitable for being connected to the momentary operation valve of turbogenerator.In the exhaust casing, the opening member (3) is attached on the lantern ring (4) and is formed the extension of hollow arm (63), so that the air stream (7) left from the outlet (30) of momentary operation valve passes through hollow arm (63) and flow in the hub (5).

Description

Turbine engine exhaust shell with improved service life
Technical field
The present invention relates to a kind of turbine engine exhaust shell for aircraft, the uses of the turbine engine exhaust shell Service life is increased.
More precisely, the present invention relates to a kind of following exhaust casing, which makes by the exhaust casing The power that temperature difference between cover and hub generates can be limited.
Background technique
The service life of exhaust casing (or turbine rear frame (Turbine Rear Frame, TRF)) is by by described The height for the power that temperature difference between the cover and hub of exhaust casing generates influences.Outer cup is especially being connected to inside by these power It is generated at the arm of hub.
Therefore, in take off period or the boost phase of aircraft, cover is heated much more rapidly compared to bigger hub, and the two This temperature difference between component will cover generation tension at the arm for being connected to hub, because under the influence of heat, cover is faster than hub Ground expansion.
On the contrary, cover is quickly cooled down than hub when turbine stops, therefore produced at the arm for being connected to hub that will cover Raw compressing force.
Summary of the invention
An overall goal of the invention is to propose that a kind of following scheme, the program make by the temperature between cover and hub The power that degree difference generates can be limited, to increase the service life for the arm that cover is connected to hub, to increase entire exit casing The service life of body.In addition, the program must be simple so as to be readily applied on aircraft turbine engine, without A large amount of extra cost can be incurred.
In particular, according in a first aspect, being vented the invention proposes a kind of exhaust casing for aircraft turbine engine Shell includes cover, the hub for forming cavity, described cover is connected to the hollow arm and at least one oral area of the hub, this is at least One oral area is located at cover above and is suitable for being connected to the outlet of the momentary operation valve of turbogenerator, which is characterized in that institute It states at least one oral area and is attached to cover in the extension of hollow arm, so that the air exited from the outlet of momentary operation valve It flows through in hollow arm and circulates in the cavity of hub.
This device makes it possible to be limited in the takeoff phase of aircraft or the phase of boost phase by making the hub heating Between hub and cover between temperature difference so that the service life of exhaust casing can increase.
According to additional feature, exhaust casing includes at least one yoke arms, and adjacent with the yoke arms hollow Arm includes deflector, to make to deflect from the air stream that the hollow arm exits towards the reinforcing member of yoke arms.
According to the feature of supplement, the hollow arm adjacent with yoke arms includes reinforcing member, which includes side port, and And deflector is located in the reinforcing member of the hollow arm, to wear at least part of the air stream exited from the hollow arm The reinforcing member for crossing the side port towards yoke arms deflects.
According to specific feature, the hollow arm adjacent with yoke arms includes reinforcing member, which includes preceding aperture, and Deflector is located at the preceding aperture.
According to another feature, deflector is curved sheet metal part.
According to additional feature, exhaust casing is the exhaust casing with tangential arm.
According to second aspect, the invention proposes a kind of turbogenerator, which includes one in preceding feature Exhaust casing described in, wherein the turbogenerator includes instantaneous vent valve, which includes outlet, should Outlet is connected to the oral area of the exhaust casing.
According to the third aspect, the invention proposes a kind of aircraft, which includes the turbogenerator according to preceding feature.
Detailed description of the invention
With reference to the attached drawing provided with non-limiting example, by reading following detailed description, other of the invention are special Sign, objects and advantages will become more fully apparent, in the accompanying drawings:
Fig. 1 a shows the perspective view of exhaust casing according to first embodiment；
Fig. 1 b shows view identical with Fig. 1 a, but the outlet of instantaneous vent valve have been not shown so that oral area more Add obvious；
Fig. 2 shows the views in the section of exhaust casing according to first embodiment；
Fig. 3 shows the detailed view of the reinforcement of the arm for connecting cover with hub of modification according to first embodiment, Wherein the reinforcing member of arm only includes a preceding aperture；
Fig. 4 shows the detailed view of the reinforcement of the arm for connecting cover with hub of another modification according to first embodiment Figure, wherein the reinforcing member of arm includes side port；
Fig. 5 shows the more detailed view of Fig. 4 of the modification of first embodiment, and wherein reinforcing member includes side hole Mouthful；
Fig. 6 shows the view in the section of exhaust casing according to the second embodiment.
Specific embodiment
It is the first embodiment of exhaust casing 2 shown in Fig. 1 a and Fig. 1 b, which is attached with airplane turbine hair The outlet 30 of the momentary operation valve (alternatively, instantaneous vent valve (Transient Bleed Valve, TBV)) of motivation.
Exhaust casing 2 includes the cover 4 connected by multiple arms 6 and hub 5 and oral area 3, and oral area 3 is located on cover 4, forms number The extension of a arm 6.Hub 5 includes cavity at its center.
In this multiple arm 6, exhaust casing 2 includes (the represented implementation in Fig. 1 a, Fig. 1 b and Fig. 2 of yoke arms 61 It is three in example), yoke arms 61 are arranged to aircraft at the attachment element 41 of cover 4.These yoke arms 61 are the arms of non-hollow 6, and be the arm 6 for the mechanical strength that ensure that exhaust casing 2.Yoke arms 61 are not linked to any oral area 3.There is no oral area 3 Cover 4 is attached in the extension of yoke arms 61.
Exhaust casing 2 further includes oily sub-arm (oil utility arms) 62, is equipped with oil stream in oily sub-arm 62 Logical circuit, oily flow cycle supply the hydraulic circuit for controlling ancillary equipment (such as, wing flap, brake, take-off and landing device).? In embodiment shown in Fig. 2, exhaust casing 2 includes three oily sub-arms 62, these three oily sub-arms 62 are disposed in about hub 5 The opposite of three yoke arms 61.Oily sub-arm 62 is not linked to any oral area 3.There is no oral area 3 in the extension of oily sub-arm 62 Cover 4 is attached in portion.
Finally, exhaust casing 2 further includes hollow arm 63, each hollow arm 63 includes cavity, and cavity is beaten two ends It opens, therefore is opened at cover 4 and hub 5.In the first embodiment, all hollow arms 63 are connected to oral area 3.More precisely, Oral area 3 in the extension of each hollow arm 63 (such as passing through welding) is applied to cover 4, so that when outlet 30 is attached to When oral area 3, the air stream 7 exited from the outlet 30 is formed directly into the cavity of hollow tube 63.Oral area 3 is that one kind is applied Component (applied part), which is attached to the cover 4 of exhaust casing 2, and can ensure outlet 30 attachment and its sealing on cover 4.
As shown in Fig. 2, the outlet 3 of momentary operation valve is each connected to hollow arm 63 by oral area 3, so that from instantaneous The air stream 7 that operation valve exits is penetrated in hollow arm 63 and is circulated in hub 5, and is more precisely flowed in the cavity of hub 5 It is logical.
Momentary operation valve, which is a kind of high-pressure compressor for enabling turbogenerator, to be started and acceleration period is exhausted Valve, air stream 7 is the stream of hot air for enabling hub 5 to be heated, to limit the phase taken off with boost phase in aircraft Between hub 5 and cover 4 between temperature difference.
Therefore, the tension occurred at arm 6 during the takeoff phase of aircraft or boost phase is limited, and is vented Therefore the service life of shell 2 is increased.
Advantageously, although the oil flow cycle present in oily sub-arm 62 is heated by air stream 7, the wind of oily coking Danger not will increase.In fact, high-pressure compressor only passes through momentary operation during the starting stage of aircraft or boost phase Valve is exhausted, and oil will not be heated during its not period of recirculation, to will not increase the risk of coking.
Therefore, this can be easily implemented on turbogenerator, without expensive adaptation sex work, and will not The problem of for turbogenerator with coming oil coking.In fact, being connected with outlet 30 generally on known turbogenerator Oral area 3 be disposed on the cover 4 of exhaust casing 2, air stream 7 to be evicted between cover 4 and the arm 6 that connects of hub 5.Cause This, it is only necessary to exhaust casing 2 is slightly adapted to.
In the first embodiment of the present invention, in order to improve hub 5 heating uniformity, and as shown in Fig. 2, leaving in A part of the air stream 7 of empty arm 63 is directed towards the region for being attached with yoke arms 61 of hub 5.In fact, the hub 5 It is not heated by the stream of hot air 7 that the arm 6 being attached from hub exits directly in the region.
Arm 6 respectively includes reinforcing member 60, and reinforcing member 60 is located in hub 5.As shown in Fig. 2, air stream 7 at reinforcing member 60 from Open hollow arm 63.
In this embodiment, the air stream 7 left from the hollow arm 63 adjacent with yoke arms 61 passes through deflector 8 towards institute The reinforcing member 60 for stating yoke arms 61 deflects.Deflector 8 can be implemented by curved sheet metal part, the curved lamellar gold Belong to component to be disposed at the reinforcing member 60 of the hollow arm 63 adjacent with the yoke arms 61.
In first embodiment shown in Fig. 2, three yoke arms 61 are continuously arranged so that only two hollow arms 63 with Yoke arms 61 are adjacent.
First modification according to first embodiment, being shown in FIG. 3, the enhancing of the hollow arm 63 adjacent with yoke arms 61 Part 60 includes two lateral sidewalls 600, the two lateral sidewalls 600 formed include preceding aperture 601 channel, air stream 7 is from hollow The preceding aperture 601 is passed through when arm 63 exits to flow.Preceding aperture 601 is located in the extension of the cavity of hollow arm 63.
In the first modification of first embodiment, deflector 8 is disposed at preceding aperture 601, to make 7 direction of air stream The reinforcement 60 of yoke arms 61 deflects.
The second modification that is according to first embodiment, showing in figures 4 and 5, lateral sidewall 600 respectively include side port 602 (only one side port 602 is shown in figures 4 and 5).Therefore, deflector 8 is located at side port in reinforcement 60 At 602, and so that air stream 7 is passed through side port 602 and deflected towards yoke arms 61.
Preferably, in the first embodiment, the air stream 7 exited from hollow arm 63 not directly faces oily sub-arm 62 partially Turn, in order to avoid cause oil overheating.
According to second embodiment shown in Fig. 6, air stream 7 is not through the increasing that deflector 8 is directly toward yoke arms 63 Strong part 60 deflects.In fact, when exhaust casing 2 is tangential arm housing, in cavity of the uniformity of the heating of hub 5 by hub 5 The vortex 9 (or whirlpool) of hot-air ensures.Exhaust casing with tangential arm is herein understood as shell as described below, The arm of the shell about hub outer surface about normal slope.
Therefore, about the outer surface of hub 5 about normal slope, air stream 7 about normal slope reaches in hub 5 arm 6 Portion, this forms vortex 9 under the influence of the centrifugal force.

Claims (7)

1. being used for the exhaust casing of aircraft turbine engine, the exhaust casing includes cover (4), the hub (5) for forming cavity, by institute Hollow arm (63) and at least one oral area (3) that cover (4) is connected to the hub (5) are stated, at least one described oral area is located at institute State on cover (4) and be suitable for being connected to the outlet (30) of the momentary operation valve of the turbogenerator, it is described at least one Oral area (3) is attached to the cover (4) in the extension of hollow arm (63), so that from the outlet of the momentary operation valve (30) air stream (7) exited is penetrated in the hollow arm (63) and is circulated in the cavity of the hub (5), and feature exists In the exhaust casing (2) includes at least one yoke arms (61), and the hollow arm (63) adjacent with the yoke arms (61) is wrapped Deflector (8) is included to make first reinforcing member of the air stream (7) exited from the hollow arm (63) towards the yoke arms (61) Deflection.
2. exhaust casing (2) according to claim 1, which is characterized in that in adjacent described of the yoke arms (61) Empty arm (63) includes the second reinforcing member, and second reinforcing member includes side port (602), and, the deflector (8) is located at In second reinforcing member of the hollow arm (63), to make at least part of the air stream (7) exited from the hollow arm (63) The first reinforcing member across the side port (602) towards the yoke arms (61) deflects.
3. exhaust casing (2) according to claim 1, which is characterized in that in adjacent described of the yoke arms (61) Empty arm (63) includes the second reinforcing member, and second reinforcing member includes preceding aperture (601), and the deflector (8) is located at this At preceding aperture (601).
4. according to claim 1 to exhaust casing (2) described in one in 3, which is characterized in that the deflector (8) is bending Sheet metal part.
5. according to claim 1 to exhaust casing (2) described in one in 3, which is characterized in that the exhaust casing (2) is tool Have an exhaust casing of arm, the arm about the hub outer surface about normal slope.
6. a kind of turbogenerator, the turbogenerator includes according to claim 1 to exhaust casing described in one in 5 (2), wherein the turbogenerator includes instantaneous vent valve, and the instantaneous vent valve includes outlet (30), the outlet quilt It is connected to the oral area (3) of the exhaust casing (2).
7. a kind of aircraft, the aircraft includes turbogenerator according to claim 6.
CN201680042755.5A 2015-07-21 2016-07-20 Turbine engine exhaust shell with improved service life Active CN107849983B (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1556893A FR3039207B1 (en) 2015-07-21 2015-07-21 EXHAUST CASE OF A TURBOMACHINE WITH INCREASED LIFETIME
FR1556893 2015-07-21
PCT/FR2016/051870 WO2017013356A1 (en) 2015-07-21 2016-07-20 Turbine engine exhaust casing with improved lifetime

Publications (2)

Publication Number Publication Date
CN107849983A CN107849983A (en) 2018-03-27
CN107849983B true CN107849983B (en) 2019-05-28

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Country Status (9)

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US (1) US10648366B2 (en)
EP (1) EP3325788B1 (en)
JP (1) JP6785837B2 (en)
CN (1) CN107849983B (en)
BR (1) BR112018001163B1 (en)
CA (1) CA2991740C (en)
FR (1) FR3039207B1 (en)
RU (1) RU2722514C2 (en)
WO (1) WO2017013356A1 (en)

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EP3325788A1 (en) 2018-05-30
CN107849983A (en) 2018-03-27
JP2018524520A (en) 2018-08-30
FR3039207B1 (en) 2019-07-26
US20180195416A1 (en) 2018-07-12
BR112018001163B1 (en) 2022-11-16
CA2991740A1 (en) 2017-01-26
FR3039207A1 (en) 2017-01-27
RU2018106238A (en) 2019-08-21
JP6785837B2 (en) 2020-11-18
BR112018001163A2 (en) 2018-09-18
EP3325788B1 (en) 2019-08-28
RU2722514C2 (en) 2020-06-01
US10648366B2 (en) 2020-05-12
RU2018106238A3 (en) 2019-12-02
CA2991740C (en) 2023-07-25
WO2017013356A1 (en) 2017-01-26

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